CN207482177U - A kind of Multifunctional navigation aircraft windshield - Google Patents
A kind of Multifunctional navigation aircraft windshield Download PDFInfo
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- CN207482177U CN207482177U CN201721460797.9U CN201721460797U CN207482177U CN 207482177 U CN207482177 U CN 207482177U CN 201721460797 U CN201721460797 U CN 201721460797U CN 207482177 U CN207482177 U CN 207482177U
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- glassy layer
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Abstract
The utility model is related to a kind of Multifunctional navigation aircraft windshields, it includes organic film layers, the outer glassy layer being set on the outside of organic film layers, is set on the inside of organic film layers and the interior glassy layer opposite with outer glassy layer, organic film layers that setting is mutually bonded, the frame of outer glassy layer and interior glassy layer and the bonded adhesives that is filled between organic film layers, outer glassy layer and interior glassy layer and frame, it is characterized in that, organic film layers are equipped with heating unit with outer glass interlayer, and organic film layers are equipped with electromagnetic protective device with interior glass interlayer.The aviation aircraft of the application hits anti-splashing structure with windshield equipped with heating unit, electromagnetic protective device and anti-bird, and windshield is made to have the function of that anti-icing demisting, electromagnetic protection and anti-bird are hit.
Description
Technical field
The utility model is related to a kind of technical fields of aviation aircraft glass more particularly to a kind of Multifunctional navigation to fly
Device windshield.
Background technology
The transparent region generally use full-inorganic glass structure of the windshield of aviation aircraft or full stress-strain are compound at present
Structure is adhered on aircraft window frame with structure glue or is fixed on aircraft window frame with screw, rivet etc..
When the transparent region of windshield uses full stress-strain composite construction, since windshield will bear rain brush repeatedly
It scratches, the damage resistant ability of organic composite structure is well below the damage resistant ability of full-inorganic glass structure.Although organic composite
Structure can be hardened by outer surface increases scratch resistance capability, but still have larger gap, longevity compared with full-inorganic glass structure
Life is shorter.
When the transparent region of windshield uses full-inorganic glass structure, full-inorganic glass structure has excellent damage resistant
Ability, and its bonding force between film is preferable.Outer glassy layer use unorganic glass realize scratch resistance, anti-rain brush scratch with
It is and preferably environment resistant.It can increase anti-bird by pasting anti-splashing film at unorganic glass inner surface and hit performance.Full-inorganic glass knot
Structure has the advantages such as long lifespan, reliability height.
At present, the windshield of aviation aircraft causes its molding more difficult due to size is big and curved surface radian is big, together
When its weight demands it is also very harsh, therefore windshield must light thin type.More wanted because of the shock resistance of windshield
Ask higher, it is desirable to be able to which the aerodynamic loading and bird born in-flight hits impact.When aviation aircraft by flying bird in in-flight hitting
When hitting, windshield cannot breakdown and glass back cannot there is splash to make facility in driver and aviation aircraft cabin
Into injury.It is also more and more to the performance requirement of aviation aircraft windshield with the development of technology, such as electrical heating is anti-icing
Defrosting function, electromagnetic protection function etc..
Utility model content
For deficiency of the prior art, the purpose of this utility model is to provide a kind of Multifunctional navigation aircraft windscreen
Glass.
In order to solve the above-mentioned technical problem, this application discloses a kind of Multifunctional navigation aircraft windshield, packets
Include organic film layers, the outer glassy layer being set on the outside of organic film layers, be set on the inside of the organic film layers and with
The opposite interior glassy layer of the outer glassy layer, setting be mutually bonded organic film layers, outer glassy layer and interior glassy layer frame and
The bonded adhesives being filled between organic film layers, outer glassy layer and interior glassy layer and the frame, which is characterized in that the organic gel
Lamella is equipped with heating unit with outer glass interlayer, and organic film layers are equipped with electromagnetic protective device with interior glass interlayer.
According to the embodiment of the application, above-mentioned heating unit includes electric heating film and connects leading for the electric heating film
Electric item, the electric heating film are set to the inside of the outer glassy layer, and positioned at organic film layers and outer glass interlayer；Institute
Conductive bar is stated between organic film layers and electric heating film, and the edge of the close outer glassy layer, the conductive bar
Conductor wire is led to outside the frame.
According to the embodiment of the application, above-mentioned electromagnetic protective device includes screened film, screening conductive item and gauze screen,
The screened film is set to the inside of the interior glassy layer, and the screening conductive item connects the screened film, and close to described interior
The edge of glassy layer；One end of the gauze screen connects the screening conductive item, and leads to outside the frame.
According to the embodiment of the application, above-mentioned electromagnetic protective device further includes separation layer, and the separation layer is set to
The screened film.
Above-mentioned to further include anti-splashing film layer according to the embodiment of the application, the anti-splashing film layer is set to described
Separation layer, material PET.
According to the embodiment of the application, the material of above-mentioned interior glassy layer and outer glassy layer is full-inorganic glass material,
Through intensive treatment, the thickness of the interior glassy layer and outer glassy layer is no more than 1.8mm respectively for the interior glassy layer and outer glassy layer.
Compared with prior art, the application can be obtained including following technique effect：
The application discloses a kind of Multifunctional navigation aircraft windshield, is equipped with heating unit, heating unit is to wind
Gear glass is heated, and windshield is made to have the function that anti-icing demisting, is realized and is provided under any meteorological condition to driver
One broad enough, clear and distortionless visual field.
The aviation aircraft of the application is further provided with electromagnetic protective device with multi-functional windshield, and windshield is made to have electricity
Magnetic safeguard function, avoids driver from being injured by electromagnetism.
The aviation aircraft of the application is further provided with anti-bird with multi-functional windshield and hits anti-splashing structure, and structure is light
It is thin, it being capable of loss of weight.
Description of the drawings
Fig. 1 is the schematic diagram of the aviation aircraft windshield of one embodiment of the application.
Fig. 2 is the partial cutaway view of the aviation aircraft windshield of one embodiment of the application.
Specific embodiment
The multiple embodiments for the application being disclosed with schema below, as clearly stated, the details in many practices
It will be explained in the following description.It should be appreciated, however, that the details in these practices is not applied to limit the application.Also
It is to say, in some embodiments of the application, the details in these practices is non-essential.In addition, for the sake of simplifying schema,
Some known usual structures will be painted it in a manner of simply illustrative in the drawings with component.
About its " first " used herein, " second " etc., the meaning of order or cis-position is not especially censured, also non-use
The component described with identical skill term just for the sake of difference with to limit the application or operation.
Please refer to Fig.1 and Fig. 2, be the aviation aircraft windshield 1 of one embodiment of the application schematic diagram and
Partial cutaway view；As shown in the figure, present embodiment provide a kind of aviation aircraft windshield 1 include organic film layers 10,
Interior glassy layer 11, outer glassy layer 12, frame 13 and bonded adhesives 14, interior glassy layer 11 are set to the inside of organic film layers 10, outside
Glassy layer 12 is set to the outside of organic film layers 10, and opposite with interior glassy layer 11, frame 13 have the first wears groove 131 and with
Second wears groove 132 of the first wears groove 131 connection, the organic film layers 10 being mutually bonded, interior glassy layer 11 and outer glassy layer 12 are set
In in the first wears groove 131 of frame 13, one end of organic film layers 10 is extended in the second wears groove 132.Bonded adhesives 14 is filled in
In first wears groove 131 and the second wears groove 132, i.e., positioned at organic gel lamella 10, interior glassy layer 11 and outer glassy layer 12 and frame 13
Between.The interior glassy layer 11 of present embodiment and the material of outer glassy layer 12 are using full-inorganic glass material, interior glassy layer 11 and outer
For glassy layer 12 through intensive treatment, the thickness of interior glassy layer 11 and outer glassy layer 12 is no more than 1.8mm respectively, and with excellent resistance to
Scuffing ability.Between interior glassy layer 11 and outer glassy layer 12 and organic film layers 10 there is good bonding force, have enough glue
Connect intensity.Interior glassy layer 11 and the stress load of outer glassy layer 12 and the deformation quantity of thermal force are almost consistent, will not lead to interior glass
With organic film layers 10 lamination defect occurs for glass layer 11 and outer glassy layer 12.
The aviation aircraft windshield 1 of present embodiment is characterized in that.Organic film layers 10 and outer glassy layer 12
Between be equipped with heating unit 15, heating unit 15 include electric heating film 151 and connect electric heating film 151 conductive bar 152, electrical heating
Film 151 is set to the inside of outer glassy layer 12, and between organic film layers 10 and outer glassy layer 12.Conductive bar 152, which is located at, to be had
Between machine film layers 10 and electric heating film 151, and close to the edge of outer glassy layer 12, the conductor wire 1521 of conductive bar 152 leads to side
Outside frame 13, to connect power supply.When providing power supply to conductive bar 152 by conductor wire 1521, electric heating film is connected in conductive bar 152
151, electric heating film 151 heats windshield 1, promotes the anti-icing demisting ability of windshield 1, realizes in any meteorological condition
Under give driver provide a broad enough, clear and distortionless visual field.
The windshield 1 of present embodiment further includes the electromagnetic protection being set between interior glassy layer 11 and organic film layers 10
Device 16, electromagnetic protective device 16 include screened film 161, screening conductive item 162 and gauze screen 163, and screened film 161 is set to interior
The inside of glassy layer 11, screening conductive item 162 connect screened film 161, and close to the edge of interior glassy layer 11.Gauze screen 163
One end connection screening conductive item 162, and led to by the second wears groove 132 and overlapped outside frame 13 with the fuselage of aviation aircraft,
So that the windshield 1 of present embodiment has the function of electromagnetic protection, driver is avoided to be injured by electromagnetism.Present embodiment
Electromagnetic protective device 16 further include separation layer 164, separation layer 164 is set to screened film 161.
The windshield 1 of present embodiment further includes anti-splashing film layer 17, and anti-splashing film layer 17 is set to interior glassy layer 11
Inner surface, in present embodiment, anti-splashing film layer 17 is set to separation layer 164, material PET.Present embodiment
Anti-splashing film layer 17 has good non-brittle tensile property, and when windshield 1 is by bird strike, anti-splashing film layer 17 is logical
It crosses deformation and absorbs Impact energy, windshield 1 is avoided to generate splash due to rupture.
In conclusion the application discloses a kind of Multifunctional navigation aircraft windshield, it is equipped with heating unit, heating
Device heats windshield, and windshield is made to have the function that anti-icing demisting, realizes under any meteorological condition to driving
The person of sailing provides a broad enough, clear and distortionless visual field.The aviation aircraft of the application is further provided with electricity with windshield
Magnetic protective device makes windshield have electromagnetic protection function, driver is avoided to be injured by electromagnetism.And its anti-bird hits anti-fly
It splashes design structure and realizes that windshield has weight frivolous and can bear aerodynamic loading and bird hits impact so that windscreen glass
Glass cannot be breakdown without splash, and driver is avoided to come to harm.
The upper only presently filed embodiment, is not limited to the application.For those skilled in the art
For, the application can have various modifications and variations.All any modifications made in spirit herein and principle are equal
Replace, improve etc., it should all be included within the scope of claims hereof.
Claims (6)
1. a kind of Multifunctional navigation aircraft windshield including organic film layers, is set to outside organic film layers
The outer glassy layer of side is set on the inside of the organic film layers and the interior glassy layer opposite with the outer glassy layer, setting mutually glue
The frame of the organic film layers, outer glassy layer and the interior glassy layer that connect and it is filled in organic film layers, outer glassy layer and interior glass
Bonded adhesives between glass layer and the frame, which is characterized in that organic film layers are equipped with heating unit, institute with outer glass interlayer
It states organic film layers and is equipped with electromagnetic screen with interior glass interlayer.
2. aviation aircraft windshield according to claim 1, which is characterized in that the heating unit includes electricity and adds
The conductive bar of hotting mask and the connection electric heating film, the electric heating film are set to the inside of the outer glassy layer, and positioned at institute
State organic film layers and outer glass interlayer；The conductive bar is between organic film layers and electric heating film, and close to described
The edge of outer glassy layer, the conductor wire of the conductive bar are led to outside the frame.
3. aviation aircraft windshield according to claim 1, which is characterized in that the electromagnetic protective device includes
Screened film, screening conductive item and gauze screen, the screened film are set to the inside of the interior glassy layer, and the screening conductive item connects
The screened film is connect, and close to the edge of the interior glassy layer；One end of the gauze screen connects the screening conductive item, and draws
Outside to the frame.
4. aviation aircraft windshield according to claim 3, which is characterized in that the electromagnetic protective device more wraps
Separation layer is included, the separation layer is set to the screened film.
5. aviation aircraft windshield according to claim 4, which is characterized in that further include anti-splashing film layer, institute
It states anti-splashing film layer and is set to the separation layer, material PET.
6. aviation aircraft windshield according to claim 1, which is characterized in that the interior glassy layer and outer glass
The material of layer is full-inorganic glass material, the interior glassy layer and outer glassy layer through intensive treatment, the interior glassy layer and outer glass
The thickness of glass layer is no more than 1.8mm respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721460797.9U CN207482177U (en) | 2017-11-06 | 2017-11-06 | A kind of Multifunctional navigation aircraft windshield |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721460797.9U CN207482177U (en) | 2017-11-06 | 2017-11-06 | A kind of Multifunctional navigation aircraft windshield |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207482177U true CN207482177U (en) | 2018-06-12 |
Family
ID=62475550
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721460797.9U Active CN207482177U (en) | 2017-11-06 | 2017-11-06 | A kind of Multifunctional navigation aircraft windshield |
Country Status (1)
| Country | Link |
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| CN (1) | CN207482177U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109862639A (en) * | 2019-03-26 | 2019-06-07 | 北京航天发射技术研究所 | A kind of glass with electric heating and function of shielding |
| CN109917349A (en) * | 2019-04-04 | 2019-06-21 | 山东富锐光学科技有限公司 | A kind of scanning laser radar |
| CN110254743A (en) * | 2019-05-17 | 2019-09-20 | 陕西飞机工业（集团）有限公司 | A kind of cockpit side windshield assembly method and assembly skeleton |
| CN111891333A (en) * | 2020-07-08 | 2020-11-06 | 中国航发北京航空材料研究院 | Bearing type multifunctional electric heating windshield |
-
2017
- 2017-11-06 CN CN201721460797.9U patent/CN207482177U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109862639A (en) * | 2019-03-26 | 2019-06-07 | 北京航天发射技术研究所 | A kind of glass with electric heating and function of shielding |
| CN109862639B (en) * | 2019-03-26 | 2021-12-07 | 北京航天发射技术研究所 | Glass with electric heating and shielding functions |
| CN109917349A (en) * | 2019-04-04 | 2019-06-21 | 山东富锐光学科技有限公司 | A kind of scanning laser radar |
| CN109917349B (en) * | 2019-04-04 | 2021-11-19 | 山东富锐光学科技有限公司 | Scanning laser radar |
| CN110254743A (en) * | 2019-05-17 | 2019-09-20 | 陕西飞机工业（集团）有限公司 | A kind of cockpit side windshield assembly method and assembly skeleton |
| CN110254743B (en) * | 2019-05-17 | 2023-06-23 | 陕西飞机工业（集团）有限公司 | Cabin side windshield assembly method and assembly framework |
| CN111891333A (en) * | 2020-07-08 | 2020-11-06 | 中国航发北京航空材料研究院 | Bearing type multifunctional electric heating windshield |
| CN111891333B (en) * | 2020-07-08 | 2024-04-09 | 中国航发北京航空材料研究院 | Bearing type multifunctional electric power up Wen Fengdang |
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